Apparatus and method for gyroscopic propulsion

ABSTRACT

Disclosed is a combination of six substantially identical interconnected rotating masses, with a pair each of the rotating masses being configured to rotate in one of each of the three planes (X, Y, and Z). Regardless of the orientation of the six masses, each pair of the six interconnected rotating masses may share substantially the same center of gravity and generate a separate yet interactive kinetic energy and angular momentum in each of the three planes, thereby providing resistance to rotational forces from external sources. This is known as “equal force presence.” In one embodiment, the rotating masses are ring-like masses. In alternative embodiment, the rotating masses are solid masses, similar to flywheels.

RELATED APPLICATIONS

This application is a divisional of U.S. patent application Ser. No.12/136,047, filed on Jun. 9, 2008, which application is now pending andwhich application is a continuation in part of U.S. patent applicationSer. No. 11/581,809, filed on Oct. 16, 2006, which application is nowissued as U.S. Pat. No. 7,383,747 and which application is a divisionalof U.S. patent application Ser. No. 10/770,795, filed on Feb. 3, 2004,now issued as U.S. Pat. No. 7,121,159 and which patent is acontinuation-in-part of U.S. patent application Ser. No. 10/087,430,filed on Mar. 1, 2002, now issued as U.S. Pat. No. 6,705,174, all ofwhich are incorporated herein by reference.

BACKGROUND OF THE INVENTION

1. Technical Field

The present invention relates generally to rotational forces and morespecifically relates to creating a linear movement from a system ofrotational forces.

2. Background Art

Propulsion of an object not in contact with a relatively fixed body, forexample the ground or a planet surface, is generally obtained only bymovement of air or other gases in a direction substantially opposite tothe movement of the object under the effect of the propulsion systems.In the absence of a suitable atmosphere, for example in space,propulsion is generally obtained by rocket systems or by other similarsystems which involve the projection of particles at high velocity fromthe object, in the opposite direction of the object's intended travel.Such systems, by their very nature and design, require the consumptionof significant quantities of fuel since the fuel or the byproducts ofthe consumption or expulsion of the fuel forms the particles to beprojected.

Attempts have been made for many years to develop a propulsion system,which generates linear movement from a rotational drive. Examples ofthis type of arrangement are shown in a book entitled “The Death ofRocketry” published in 1980 by Joel Dickenson and Robert Cook.

However none of these previous arrangements has in any way provedsatisfactory and if any propulsive effect has been obtained this hasbeen limited to simple models. One of the problems with the previousattempts is the limited understanding of the true nature of the laws ofmotion and the nature of the physical universe. The laws of motion, ascurrently defined and used in the scientific community, are onlyaccurate to a limited degree of precision. Many conditions andqualifications are required to apply them to the physical world, as itactually exists. This is far truer for the quantification of angularmotion than it is for more linear motion. The laws of motion postulatedby Newton are built upon his first law of inertia and are generallyregarded as the foundation of Einstein's theory of relativity.

In the cosmos, everything is moving and there is no object that isperfectly static and motionless. The very first law of physics involvesconcepts that are only proper in a given frame of reference. Consider abody “at rest.” The idea of “at rest” implies a lack of motion. However,the object is only “at rest” with respect to the relative motion of theobject's immediate environment. Matter “at rest” is actually moving inpatterns of motion that create the appearance of static motionlessness,yet the accumulated energies within the matter, in addition to therelative motion of the composite cosmic environment, is well known andprovides sufficient evidence that everything is in a state of constantmotion. Inertia, as it is generally referred to in relation to the lawsof physics, represents relatively balanced force relationships creatingrelatively constant and stable motion patterns.

The basic formulas typically used to describe various angular forces aresufficient to explain only the most basic concepts relative to thebehavior of spinning masses. They are the accepted formulas of Newtonianphysics for linear motion applied to rotation with the linear componentsexchanged for angular ones. Rotational inertia is generally defined withthe appropriate embellishments necessary to include the shape of themass about the axis of rotation as an additional factor in the magnitudeof the inertia.

Newton's first law of motion dealing with inertia and the inertialreference frames used in the calculation of linear forces do not, in thestrictest sense, apply to rotational force associations. Inertialreference frames are usually linear by qualification and rotating framesof reference are never inertial. This fact is not a significant factorto include in the calculations of most linear forces. In most cases ofordinary motion, the angular components in the inertial reference frameare negligible. For example, air resistance is frequently a negligiblefactor in certain cases and, in those cases, can therefore be ignored.Or as the limitations of the linear velocity of things is ignored unlesssufficiently close to the recognized maximum. Similarly, the non-linearcomponents of most inertial reference frames ignored, and can be, formost ordinary kinds of motion. The additional factor of shape foreverqualifies the angular motion aspects of particle associations withrespect to the force of that association. This is the most meaningfuland valuable factor separating the behavior of angular force from linearforce.

Motion on a scale large enough with respect to the earth and the cosmicenvironment to be substantially non-linear can never be ignored. Andthis is not the case with most kinds of ordinary motion. In thefundamentals of physics, this fact is considered significant only forlarge-scale motions such as wind and ocean currents, yet “strictlyspeaking” the earth is not an inertial frame of reference because of itsrotation. The earth's non-linear character is observed in the case ofthe Foucault pendulum, the Coriolis Effect, and also in the case of afalling object which does not fall “straight” down but veers a little,with the amount of deviation from its path dependant on the period oftime that elapses during the fall. All events are subject to this factto a greater or lesser extent.

The mathematical purpose of inertial reference frames is to isolate amotion event in order to identify force components. Acceleration willonly be observed in systems that have a net force in a given directionand are not balanced or zero. Since this is only valid for the linearcomponents of motion, it works well for all kinds of motion phenomenathat are primarily linear in nature; the associated angular componentbeing either idealized or considered negligible. Only the linear forceaspects of any of these measurements hold precisely true to the formulasof mathematics describing them. To the degree that angular components ofmotion are associated with the reference frame used for measuring andcalculating force relationships, and to the extent which these angularcomponents are not included in the formulas for calculation, is to thedegree these formulas are in error. The fact that angular referenceframes cannot and do not represent inertial reference frames indicatesthat the effect of angular force is not so easily isolated in order toidentify component effects.

Mathematical analysis of rotational forces reveals that the formulasdescribing rotational motion are also limited in additional respects.Motions that include anything more than ninety degrees of rotationcannot be used as true vectors. The fundamental technique of vectors,used to determine the composite result of the effect of multiple forces,will not work for rotational motion due to the inherent lack ofintegrity in the model. Individual angular displacements, unless theyare small, can't be treated as vectors, though magnitude and directionof rotational velocity at a particular point in time and space can begiven, which is necessary. But this alone is not sufficient, because therules of vector mathematics do not hold with regard to the order of theaddition of these forces.

If the displacement of an object is given by a series of rotationalmotions, the resulting angular position of the object is differentdepending on the order of the sequence of angular motions. Vectormathematics requires that addition be commutative (a+b+c=c+b+a). Tocalculate the motion of the precessional adjustments which multipledisturbing torques have on a spinning mass in a dynamic environmentrequires extremely complex mathematical calculations and is notaccounted for in the previous attempts to translate rotational energyinto linear movement.

The fact that these precessional adjustments can be affected by a strongmagnetic field, and that there are no mathematical formulas that includethis phenomenon as a factor of calculation, demonstrates that angularmomentum is not fully predictable by the current formulas of mathematicsand this is why there has been no true success in developing anapparatus which can efficiently and effectively use the angular momentumof a spinning mass to create a controlled linear movement.

The simple systems of motion that involve a magnitude of angularmomentum that is relatively large with respect to the mass of therotating body all exhibit nuances or nutation of precessional adjustmentnot described by the force components given by the accepted formulas ofphysics for angular motion. The Levitron is one excellent example, andthere are additional examples that reveal how the rotating systems ofmotion in the natural environment are significantly more complicatedthan is typically described by the formulas associated with thesepatterns.

When these motions are recreated, using the accepted formulas for thesepatterns, the motion is not at all like the naturally observed versionsand is sterile and fixed, lacking the nuances and nutation that exist inthe cosmic environment. The nuances and nutation of spinning motionsobserved in nature are typically complex composite angular effects ofthe local cosmic environment, down to and including the immediateangular motions of observation. This is why a typical gyroscope tends todispose its axis parallel to the earth's in an effort to achieve overalldynamic equilibrium within the total environment. All angular motion isaffected by all other angular motions, at least to some degree and aclose examination reveals that everything moving is affected to acertain extent. However, rotating systems of force generate a motionpattern that can be used to magnify this interactive effect and,therefore, reveal the influence of the cosmic environment on thesepatterns of revolving motion.

When the cosmic influences are analyzed, any and all of the motions ofanything and everything include some factor of angular displacement. Aperfectly straight line is only a concept with respect to a mathematicalidea. In reality, nothing moves in absolutely linear displacements, toone degree or another, there is typically an angular component to allmotions. Even the primarily linear trajectories associated withelectromagnetic radiation are slightly curved and this phenomenon can bereadily observed in the vast stretches of outer space. In many cases,the angular component of motion is negligible for all practical intentsand purposes, in other cases, it is the primary force of action, but inno case is it non-existent.

Gravity is the reason: the closer an object is to a strong gravitationalforce, the greater the amount of angular displacement in the surroundingmotions. Astrophysicists account for this influence on the light of faraway galaxies and describe the effect as a gravitational lens. Gravityexerts a torque on all matter within its grasp. This is a factor thatshould be included in relativity's equivalence principle to furtherqualify otherwise pure linear acceleration. The angular paths of movingbodies create the inevitability of a cosmic torque in the spatial frameof any gravitational mass.

The Coriolis Effect is a composite result of the force of gravity inassociation with the rotating circular path of any given rotatingsystem. As it is ordinarily viewed, the effect on large-scale motions onthe surface of any revolving sphere is with respect to linear latitudeuntil reaching a minimum at the poles. A critical examination will showthat the angular component of motion is the same everywhere on theplanet. Only the angle, with respect to the direction of the force ofgravity, changes from the equator to the poles. At the equator, theradius, with respect to the axis of rotation, is greatest; thismaximizes the effect on linear motions and is used to advantage whenlaunching rockets into orbit around a sphere.

This bending of motion associated with gravity is the fundamentalrequirement to achieve a universe that behaves as if having purelylinear forces on all but the largest scale of cosmic proportions. Allstraight lines of motion are ultimately elliptical curves. Accordingly,without an improved understanding of the forces associated with spinningmasses and the influence of the gravitational field that is associatedwith movement of objects in general, it will be impossible to createdevices that maximize the use of spinning masses and rotational energyto create linear motion. This means that any device which attempts toharness the kinetic energy and possible advantages based on theseprinciples will continue to be sub-optimal.

SUMMARY OF THE INVENTION

Disclosed is a combination of six substantially identical interconnectedrotating masses, with a pair each of the rotating masses beingconfigured to rotate in one of each of the three planes (X, Y, and Z).Regardless of the orientation of the six masses, each pair of the sixinterconnected rotating masses may share substantially the same centerof gravity and generate a separate yet interactive kinetic energy andangular momentum in each of the three planes, thereby providingresistance to rotational forces from external sources. This is known as“equal force presence. In one embodiment, the rotating masses arering-like masses. In alternative embodiment, the rotating masses aresolid masses, similar to flywheels.

BRIEF DESCRIPTION OF THE DRAWINGS

The preferred embodiments of the present invention will hereinafter bedescribed in conjunction with the appended drawings, wherein likedesignations denote like elements, and:

FIG. 1 is a perspective view of the three planes for initial rotation ofthe six gyroscopic rings of a gyroscopic propulsion apparatus accordingto a preferred embodiment of the present invention;

FIG. 2 is an exploded view of the three main components in a singlegyroscopic ring used in a gyroscopic propulsion apparatus in accordancewith a preferred embodiment of the present invention;

FIG. 3 is a plan view of the surface of the rotor for one of thegyroscopic rings of a gyroscopic propulsion apparatus in accordance witha preferred embodiment of the present invention;

FIG. 4 is a plan view of an external housing for the rotor of the ringof FIG. 3;

FIG. 5 is a sectional view of a portion of the bearing assembly of therotor portion of the gyroscopic ring of FIG. 3;

FIG. 6 is an exploded view of a gyroscopic propulsion unit in accordancewith a preferred embodiment of the present invention;

FIG. 7 is a perspective view of the gyroscopic propulsion unit of FIG. 6when fully assembled;

FIG. 8 is an exploded view of a gyroscopic propulsion unit in accordancewith an alternative preferred embodiment of the present invention;

FIG. 9 is an exploded view of a gyroscopic propulsion unit in accordancewith an alternative preferred embodiment of the present invention;

FIG. 10 is a perspective view of the gyroscopic propulsion unit of FIG.9 when fully assembled;

FIG. 11 is a block diagram of the control circuits for a gyroscopicpropulsion unit in accordance with a preferred embodiment of the presentinvention;

FIG. 12 is a perspective view of a vehicle incorporating a gyroscopicpropulsion unit in accordance with a preferred embodiment of the presentinvention;

DETAILED DESCRIPTION OF THE INVENTION

To use the principles of rotational energy and momentum as a mechanismof action, a device or machine needs to be created that embodies theapplication of the rotational energy and momentum. Accordingly, at leastone preferred embodiment of the present invention uses a brushlesselectric motor design built to spin a magnetically patterned ring likethe rotor of a gyroscope to provide the desired mechanism forexploitation of the principles of angular energy and angular momentum ina gravitational field. One preferred embodiment of the present inventionemploys six of these motors, positioned in parallel pairs, with eachpair of motors being positioned at right angles to the other pairs toachieve stability in a specific frame of reference.

Ring geometry of individual spinning masses is the basis to allow forthe required association of six of these masses that are equal in theirproduction of angular momentum and kinetic energy at the same angularvelocities. The result of this association will allow for the mechanicalcontrol of the net rotational inertia of the revolving mass by thecontrol of the individual rotating masses. These individual rotatingring masses are placed in pairs at 90-degree angles with respect to eachother pair so that each pair of ring masses will have force that affectsthe other rotating ring masses identically. The composite revolving masswill exhibit rotational inertia far in excess of the rotational inertiaattributed to the mass when not in this precise motion association. Thismechanically induced force of rotational inertia will manifest itself asa force to oppose the gravitational field surrounding the compositerevolving mass when it reaches the threshold magnitude for thegravitational environment of its then current placement.

The mechanism used for the demonstration of this principle is based on abrushless electrical motor designed to produce large amounts of angularmomentum in proportion to the mass of the motor. Six brushless motors ofring geometry are used to create the composite motor. Each of the sixbrushless motors is designed to produce the same amount of angularmomentum and kinetic energy at the same angular velocity. This isaccomplished by matching the material used to construct the rotorportion of the brushless motors.

These brushless motors are designed to be powerful gyroscopic actuatorsproducing large amounts of stabilizing rotational force. Each individualring rotor is a ring-like mass housed within a containment ring. Thecontainment ring is used to contain and control the mechanical spin ofthe ring rotor and is also the housing for the electrical drive coilsfor the brushless motors. In general, it is desirable that the ringrotor be engineered to be as heavy and massive as possible and that thecontainment ring be as light and of minimal mass as is possible whilestructurally rigid enough to maintain the containment of the movingrotor. The ring rotor rides on the inside surfaces of the containmentring and is supported by a series of bearings and is driven around by aseries of drive coils acting on permanent magnets mounted in the rotor.In the most preferred embodiment of the present invention, a series of 6sets of bearings is driven around by 4 drive coils acting on 6 permanentmagnets mounted in the body of the rotor.

Those skilled in the art will recognize that more or fewer bearings maybe used in this embodiment without substantially altering thefundamental concepts. Similarly, more or fewer drive coils acting onmagnets may be used without departing from the spirit and scope of thepresent invention. Additionally, the use of magnetic technology may alsobe employed to obviate the need for brushless motors. For example, themagnetic technology used in maglev train systems may be adapted for usein creating the gyroscopic ring rotors of the present invention.

The apparatus is fundamentally an engine that includes six separaterotatable gyroscopic ring rotors, where each of the six gyroscopic ringrotors is paired with another ring rotor and each pair lies in aseparate and distinct plane. In at least one preferred embodiment of thepresent invention, where each of the three planes (X, Y, and Z) isperpendicular to the other two planes. Each pair of the gyroscopic ringrotors is capable of achieving substantially the same angular momentumat substantially the same angular velocity, as is each of the other twopairs of gyroscopic ring rotors. By simultaneously spinning each of thesix gyroscopic ring rotors, the composite superstructure comprised ofthe six individual ring rotors resists rotation in any single direction.This is known as “equal force presence.”

Further, when the rate of rotation for the six spinning ring rotorsreaches the appropriate level, the composite structure of the sixassociated rings resists any change in orientation from any externalforce, including the gravitational field of the earth or other bodieslarge enough to generate a significant gravitational field. Accordingly,as the earth spins about its axis, the mechanism moves in the onlydirection possible, which is up, or away from the center of mass for thebody exerting the gravitational force. By adjusting the angular momentumof each of the rings relative to the other rings, or by adjusting therelative angle between the planes of rotation, altitudinal anddirectional changes of the apparatus can be achieved. Each of the sixgyroscopic ring rotors housed within a containment ring may be called a“gyro actuator.”

The stabilizing force exerted by each gyro actuator is positionedagainst the forces exerted by the associated gyro actuators, so that amotion feedback loop is created. This composite superstructure ofangular momentum will exhibit a resistance to any force of torque fromany direction, making for what can be called “super-additive rotationalinertia.” The rotational inertia of this composite superstructure isrelated to the angular momentums of the individual gyro actuators. Aslong as the forces of the individual rotors are correctly matched andbalanced against one another, an internal force of stabilization orequal force presence can be achieved. With a high enough level ofangular momentum, this internal force will exceed any influence ofexternal force in the surrounding environment; including the rotationaltorque associated with the force of gravity in a given gravitationalfield. Obviously, the greater the gravitational field, the greater thekinetic energy and angular momentum that will be required to overcomethe gravitational forces associated with a given environment.

Since it is desirable to maximize angular momentum with respect to mass,the suspension system housing and containing the ring rotor, and actingas an electric stator magnetically inducing the revolving motion of therotor, is constructed to be as lightweight as possible. The angularacceleration of the ring does not need to be more than the necessaryamount to increase angular velocity and momentum and, eventually, reachthe desired level. This rate of increase can be gradual, and time can begiven for this force to accumulate.

The energy put into the system is converted into the kinetic energy ofrotation, minus any loss of energy as heat due to frictional resistance.The amount of energy that can be stored within the system without largelosses due to the frictional resistance of rotation and precessionalmotion depends at least in part on the perfection of the gyro design andconstruction. If sufficiently perfect, the generation of tremendousamounts of kinetic energy can be accumulated in the form of angularmomentum. The degree of the precision of the perfection of thiscomponent, thereby minimizing frictional resistance, is a factor indetermining its efficiency and effectiveness as a gyro actuator.

If the angular momentum is sufficient, and the containment andsuspension system is sufficiently lightweight and free to move, onlybeing anchored at one point to prevent the backspin of this containmentring, each rotor ring will carry the containment ring with it,duplicating any of its secondary angular displacement. And, like a heavypendulum or a gyro compass, it will maintain its cosmic orientation inspace adjusting to a point of maximum stability until harmony with thespinning earth and the cosmic environment is achieved. The finalorientation of a free and unrestrained spinning ring gyro is with itsaxis of rotation approximately parallel to the earth's axis except thatit will be spinning in the opposite or complementary direction.

The velocity of rotation and the rotational inertia are the factors thatdetermine the magnitude of the force of the angular momentum of the ringrotor and can be calculated, after accounting for factors such asfriction and the inertia of the containment ring as retarding factors ofgenerated force, which will negatively impact the overall performance ofthe system.

The spin of a ring with minimum frictional resistance to rotation, oncestabilized with respect to gravity, if free to move in any direction,will, at a rate proportional to its ratio of angular momentum withrespect to mass, continue to adjust with respect to the environmentuntil the point of maximum stabilization is reached on a continuingbasis. This position of maximum stabilization is oriented so that theaxis of the spinning gyro is approximately parallel to the axis of thespinning earth, yet spinning in the opposite or complementary direction.Thus, the action of a ring gyro actuator with sufficient magnitude ofangular momentum will exhibit a predilection to orient itself into adefinitive position with respect to the cosmic environment in order toattain optimum stabilization with a substantial force.

With the existence of these individual gyroscope actuators, the primarycomponent exists from which a gyroscope superstructure can be built. Inone preferred embodiment of the present invention, each pair of massestakes the form of containment rings fixed in the superstructure, atninety degree angles to one another, and are locked into place withrespect to each other, roughly forming a cube shaped device in which theforces of action on the containment rings are distributed around theperiphery of the superstructure in substantially equal and symmetricalmanner with respect to the effects of the associated revolving forces.

This superstructure may then be placed in a final light, hollow, andthin, yet strong container. This composite structure will resist torquefrom any and all directions equally, so long as the individual forces ofeach component mass are equal and balanced with respect to one another.The increase in the force of angular momentum of each individualcomponent increases the resistance of the superstructure to any outsidetorque, including the overall frame of gravitational forces associatedwith the earth and other masses. The composite superstructure ofgyroscope actuators exhibits the super-additive force of maximumrotational inertia.

Knowing that the composite superstructure will resist torque from anydirection is only one consideration of the result of this compositemotion. The pairs of gyroscopes, placed in an orientation such that eachpair is offset by ninety degrees to one another in a compositesuperstructure, cannot all be simultaneously in maximum equilibrium withrespect to any cosmic environment that is held by the force of gravity,in an angular revolution, as is the case on the surface of a planet likethe earth. When in such an environment, each of the three pairs of gyroswill continue to exert their individual influences of action towardmaximum stabilization, but all the while the composite superstructurewill not be able to absorb any precessional adjustments. Any pair ofgyro actuators, by precessing to adjust to the force of torque will, ofnecessity, cause the other two pairs of gyro actuators to require thissame adjustment, doubling the problem within the composite system, thuscreating a motion feedback loop that has no resolution within thesystem.

Only by being insulated by sufficient distance from the influence ofgravity in the cosmic environment will the composite superstructure ofinterlocked gyroscopes find equilibrium. The superior resistance totorque will direct this system of motion to the environment, which isthe freest from torque exerted by the gravitational forces inherent in atypical gravitational field. The degree of the magnitude of thiscomposite force of resistance to torque is mechanically connected to,and dependent on, the individual force of each component gyroscope.Gravity is overcome when enough energy is generated by the system thatthe resistance to torque reaches a threshold resulting in a force ofdisplacement in the direction where least external force, manifesting astorque, exists. This direction is generally away from any and allgravitational sources, including planets and other bodies of masslocated within the universe.

The mass, shape, and speed of rotation are factors in the measurement ofangular momentum, but shape and mass are the most significant factors indetermining rotational inertia. This is true except in the specialcircumstance when the mass is spinning and angular momentum itselfresists any secondary force of torque or tumble against the primaryangle of rotation. Any secondary tumbling force is distributed about theperiphery of the spinning object as precessional motion that will slowthe primary velocity of rotation until a final balance of a single axisof rotation is achieved. This super-additive effect of increasedrotational inertia of the mass in every direction except the one ofprimary rotation underscores the fact that an object rotating resiststumbling; there can be only one axis of rotation.

Referring now to FIG. 1, the three different planes of initial rotationfor a gyroscopic propulsion apparatus according to a preferredembodiment of the present invention are shown. As shown in FIG. 1, afirst plane 110 is perpendicular to a second plane 120 and to a thirdplane 130. Similarly, second plane 120 is perpendicular to third plane130. Thus, each of the three planes of rotation is perpendicular to theother two planes of rotation. For the purposes of the present invention,each of the three pairs of gyroscopes will coordinate as a pair toprovide a composite ring-like rotating mass in one of each of theseplanes.

Referring now to FIG. 2, an exploded view of the basic components of agyroscopic ring 200 in accordance with a preferred embodiment of thepresent invention is shown. As shown in FIG. 2, gyroscopic ring 200includes an upper half-shell 210, a rotor element 220, and a lowerhalf-shell 230. Upper half-shell 210 and lower half-shell 230 form acontainer for rotor element 220 and are most preferably constructed froma high-strength, durable, non-metallic, light-weight material such asVespel® made by Dupont®. Upper half-shell 210 and lower half-shell 230are ring-shaped shell elements which are joined together and form acontainment ring or housing for rotor element 220. Rotor element 220 isa spinning ring-shaped mass and is most preferably constructed fromdurable metals such as titanium, stainless steel, etc. The specificdesign of the internal surfaces of the upper half-shell 210 and lowerhalf-shell 230 are described in greater detail in FIG. 20.

Rotor 220 is carefully machined such that the inner and outer diameterof rotor 220 is slightly smaller than the inner diameter of upperhalf-shell 210 and lower half-shell 230. Additionally, the overallthickness of rotor 220 is slightly less than the interior space providedwithin the housing formed by upper half-shell 210 and lower half-shell230. This allows rotor 220 to rotate rapidly yet freely within thehousing formed by the union of upper half-shell 210 and lower half-shell230. Since rotor 220 will be rotating or spinning at a high rate, it isdesired that all of the components be durable and of high-qualityworkmanship. Further detail regarding the manufacture of rotor 220,upper half-shell 210, and lower half-shell 230 is described inconjunction with FIG. 5.

Referring now to FIGS. 3 and 4, a representative gyroscopic ring 200 isshown. In order to construct a gyroscopic propulsion apparatus or unitin accordance with at least one preferred embodiments of the presentinvention, six gyroscopic rings 200 will be needed, with each of the sixrings having the same density. FIG. 3 depicts the general physicalnature of the various components of a representative rotor element 220of a representative gyroscopic ring 200 and FIG. 4 depicts the exteriorhousing of a representative gyroscopic ring 200 with a series of copperwindings 410. In the preferred embodiments of the present invention,gyroscopic ring 220 serves as the rotor of a brushless motor. Rotorelement 220 includes a series of bearings 320 and a series of magnets350.

As shown in FIG. 3, each set of bearings 320 are spaced equidistantaround the circumference of gyroscopic ring 220. Similarly, magnets 350are also spaced equidistant around the circumference of gyroscopic ring220. In the preferred embodiments of the present invention, there are anequal number of bearings 320 and magnets 350 embedded into the body ofgyroscopic ring 220. In the most preferred embodiment of the presentinvention, the number of bearings 320 is six and the number of magnets350 is also six.

Magnets 350 are embedded into the body of rotor element 220 so as tointeroperate with copper windings 410 and create the drive mechanism forthe brushless motor that propels rotor element 220 within the housing ofgyroscopic ring 200. Magnets 350 are neo-dimium ferrous boron magnets.Magnets 350 are high-grade magnets generating a magnetic force ofapproximately 4,800 gauss each. Magnets 350 are electrically connectedin sets, with each set being connected in parallel.

Bearings 320 are recessed into the body of rotor element 220 and serveto minimize the amount of surface contact area between rotor element 220and the housing of gyroscopic ring 200. In the most preferredembodiments of the present invention, bearings 320 are high-grade gyrobearings manufactured from non-magnetic stainless steel. This allowsrotor element 220 to rotate rapidly with the housing of gyroscopic ring200 with a minimal amount of loss due to friction. Bearings 320 are mostpreferably constructed from high quality stainless steel and to be asresistive to friction as possible.

In at least one preferred embodiment of the present invention, the sixrings are associated such that each pair of the six rings is capable ofbeing positioned at 90° relative to the other two pairs of rings. Inanother preferred embodiment of the present invention, the six rings arecapable of rotating around an axis and being repositioned relative tothe other rings

Referring now to FIG. 4, a plan view depicting the exterior of arepresentative gyroscopic ring 200 according to a preferred embodimentof the present invention is shown. The exterior includes copper windings410 and Hall Effect sensors 420. In at least one preferred embodiment ofthe present invention, the number of copper windings 410 is four. Eachof the four copper windings 410 is a comprised of a series of windingsof copper wire made around the body of gyroscopic ring 200 at pointsspaced 90° apart. Copper windings 410 cooperate with magnets 350 toprovide the propulsion for rotor element 220 within the housing ofgyroscopic ring 200 in a manner consistent with typical operation of abrushless motor. Additionally, copper windings 410 serve to hold upperhalf-shell 210 and lower half-shell 230 together.

In at least one preferred embodiment of the present invention, eachcopper winding 410 is made using “turns” of approximately 28 gaugecopper wire. In this embodiment of the present invention, each copperwinding 410 is approximately 1.25 inches for each layer of copperwinding 410. Approximately 14 layers of copper are wound around the bodyof gyroscopic ring 200. It is desirable to keep the weight of copperwindings 410 to a minimum yet have enough copper to create thrustsufficient to efficiently spin rotor element 220 within the body createdby upper half-shell 210 and lower half-shell 230.

Copper windings 410 operate in pairs for a single circuit and each of apair of copper windings 410 that are located opposite each other form asingle circuit. Accordingly, there are two circuits for the arrangementshown in FIG. 4. Additionally, each of the pairs of copper windings 410for each of the two circuits operates in conjunction with a single HallEffect sensor 420 to determine the location of magnets 350, therebyallowing the effective operation of the brushless motor.

Hall Effect sensors 420 are used to sense the position of magnets 350 aspart of a feedback loop, which is used to control the rate of angularvelocity for the gyroscopic rings. The use of Hall Effect sensors 420 inthe overall control of the circuit is explained in greater detail inconjunction with FIG. 8. Connected to copper windings 410 and HallEffect sensors 420 are a set of control wires. The control wires providea means for transmitting control signals to and from superstructure 700in order to cause the rotors for each of the ring-like gyroscopes torotate.

Referring now to FIG. 5, a cross-sectional view of the interior of arepresentative gyroscopic ring 200 is shown. The housing of gyroscopicring 200 is comprised of upper half-shell 210 and lower half-shell 230,joined at seam 510. A series of interior step portions 520 serve tocontain the lateral movement of rotor element 220 within the housing ofgyroscopic ring 200 as it rotates about its axis of rotation. Similarly,upper half-shell 210 and lower half-shell 230 cooperate to constrain thevertical movement of rotor element 220 within the housing of gyroscopicring 200 as it rotates about its axis of rotation. Each bearing 320comprises a pair of wheels 530 joined together by an axle 540. Axle 540is inserted through an opening formed in the body of rotor element 220.The diameter of wheels 530 is slightly larger than the thickness ofrotor element 220, thereby preventing rotor element 220 from contactingthe housing of gyroscopic ring 200 as it rotates about its axis ofrotation. When fixed in place, bearings wheels 530 are the only point ofcontact with the housing of gyroscopic ring 200 as rotor element 220rotates about its axis of rotation.

Referring now to FIG. 6, an exploded view of a gyroscopic propulsionunit 600 in accordance with a preferred embodiment of the presentinvention is shown. Gyroscopic propulsion unit 600 comprises sixgyroscopic rings 610 mounted in six ring frames 620 by a plurality offasteners 615. Fasteners 615 are used to hold gyroscopic rings 610firmly affixed to a mounting plate 621 for each ring frame 620. In atleast one preferred embodiment of the present invention, fasteners 615comprise screws or bolts.

In the most preferred embodiments of the present invention, eachgyroscopic ring 610 is substantially the same size and weight and ismanufactured from the same materials. Ring frames 620, fasteners 615,and other components of gyroscopic propulsion unit 600 are mostpreferably manufactured from the most lightweight suitable materialspossible. Since gyroscopic propulsion unit 600 is designed to providepropulsion, the overall weight of gyroscopic propulsion unit 600 shouldbe minimized to the extent practical while still achieving equal forcepresence.

In the most preferred embodiments of the present invention, ring frames620 are manufactured from a lightweight rigid material such asheavy-duty plastics or ceramics. The material should be relativelyresistant to the effects of heat. One such material is Vespel®manufactured by Dupont®. One of the goals in the design of gyroscopicpropulsion unit 600 is to maximize the mass of the rotating massesrelative to the weight of the other components of gyroscopic propulsionunit 600.

Once assembled, each ring frame 620 will house a gyroscopic ring 610 andwhen all ring frames 620 are fastened to each other, the resultingapparatus will resemble a cube. It should be noted that a center point“A” will be a center point for each of the six gyroscopic rings 610, nomatter the orientation of gyroscopic rings 610.

In the most preferred embodiments of the present invention, gyroscopicpropulsion unit 600 is housed in a housing constructed of a durable,non-metallic material such as high-strength plastic or some othersimilar material. Additionally, the housing may contain optionalapertures that allow heat to escape the interior of the housing. Giventhat the rotors contained with gyroscopic propulsion unit 600 may bespinning rapidly, thereby generating heat, it is desirable to provide away for the heat generated by the spinning masses to escape the interiorof the housing. Accordingly, as shown in FIG. 6, ventilation openingsmay be present in ring frames 620 as well.

Gyroscopic propulsion unit 600 may be fixed in position within theinterior of the housing by using a series of molded posts, containmentridges, or other means sufficient to contain gyroscopic propulsion unit600 in place within the interior of the housing. Once placed within thehousing, one or more gyroscopic propulsion device can be attached toother objects and the propulsion generated by one or more gyroscopicpropulsion devices 600 can be used to transport objects from one placeto another. This would allow the gyroscopic propulsion device(s) 600 tobe used as a propulsion apparatus or engine for a vehicle inapplications such as transporting people and shipping goods from placeto place.

In order to achieve propulsion using gyroscopic propulsion unit 600,each gyroscopic ring 610 is energized by the combination of theirrespective magnets and windings to start the rotor element containedwithin each respective gyroscopic ring spinning The actual length oftime required to “spin up” the rings is not as important as thegyroscopic rings achieving the same angular velocity and the sameangular momentum. In addition, as long as the masses housed within thegyroscopic rings are spinning at the same angular velocity, each of thegyroscopic rings will also maintain an equal kinetic energy. Thisequates to equal “force presence.”

Depending on the circumference of the gyroscopic rings, the mass of therespective rotor elements, and the angular velocity of the gyroscopicrings, gyroscopic propulsion unit 600 will reach a point of internalstabilization that will resist all outside forces, including the forceof gravity. At this point, any increase in the angular velocity of thegyroscopic rings causes gyroscopic propulsion unit 600 to resist therotational torque of the earth and seek an internal equilibrium thatcannot be reached in its present location with respect to thegravitational field of the earth, or other body of mass large enough tocreate any type of significant gravitational field. Accordingly,gyroscopic propulsion unit 600 will need to move to a new location wherethe forces of internal stabilization can be maintained. This will causegyroscopic propulsion unit 600 to move away from the earth (or othersignificant mass) to a distance where the internal stabilization ofgyroscopic propulsion unit 600 can be maintained. The distance movedwill be related to the angular momentum of the spinning masses.

The greater the angular momentum of the spinning masses, the greater thedistance gyroscopic propulsion unit 600 will need to move. Similarly, byreducing the angular velocity of the rings, gyroscopic propulsion unit600 will begin to move back towards the earth because the internalstabilization can be maintained within a smaller distance.

Similarly, movement in directions other than directly away from theearth can be achieved by varying the angular velocity of one or more ofthe gyroscopic rings to create an imbalance in the angular velocities ofthe gyroscopic rings and/or by changing the orientation of thegyroscopic rings with respect to one another.

Referring now to FIG. 7, a fully assembled gyroscopic propulsion unit600 is depicted. It should be noted that gyroscopic propulsion unit 600is connected to a computer control system (not shown this FIG.), such asthe one depicted in FIG. 11 below.

In addition to the gyroscopic propulsion unit described in FIG. 6 andFIG. 7, a similar yet different gyroscopic propulsion unit can becreated by using a series of magnetically driven flywheels acting asgyroscopic motors or actuators to achieve equal force presence. Similarto the gyroscopic propulsion unit described in FIG. 6 and FIG. 7, sixflywheels are arranged in pairs with one pair fixed to rotate in each ofthree planes and at right angles to each of the other pairs offlywheels. This preferred embodiment of the present invention hascertain advantages in manufacturing and assembly that make it wellsuited for certain application.

In this configuration, the individual motor assemblies each have an axleextending from a hub in each of the six directions making themperpendicular to each surface on the resulting cube-like gyroscopicpropulsion unit. The axle comes through the center of a back-plate wherethe back-plate is placed at substantially the same distance from thecenter hub in each case mounted on the axle with a stop or c-ring on theaxle. The back-plates have four side border-plates or flanges used tosupport the face-plate and therefore containing each of the motorassemblies.

There is an inner-spacer between the back-plate and the bearingcomponent of the rotor preventing any contact with the back-plate andthe rotor. Another outer-spacer is placed on the axle on the other sideof the flywheel and then another c-clip holding the flywheel and spacersin place. A face-plate is placed over the flywheel and spacers with theaxle extending through the face-plate so that the face-plate rests onthe side borders plates. The back-plate, side border plates, and theface plates are all held in association by screws and completely containthe flywheel and motor drive components and keeping the flywheel frommaking contact with any surface.

The motor drive components consist of four electromagnets positioned ineach corner of the assembly containment boxes that act as a motor coilassembly. Additionally, a Hall Effect sensor is positioned on one of theside-plates between the electromagnets. The flywheel component of therotor has four powerful permanent magnets (neodymium or other similarsuitable material) mounted and embedded equidistant from each other atthe periphery of the flywheel and being positioned at ninety degreeangles with respect to one another. The magnets are placed so that theelectromagnetic coils can alternately pull and push each magnet causingthe flywheel to rotate when triggered by the electrical induction of thedrive circuit. The Hall Effect sensor associated with a dedicatedcircuit is used to determine or sense the location of the magnetsembedded in the flywheel. A control circuit is used to coordinate thesensing circuit with the drive circuit to control the angularacceleration of the rotor. A computer control circuit, such as thatdiscussed below in conjunction with FIG. 11, coordinates all six of themotor circuits to operate the composite cube device.

Referring now to FIG. 8, an exploded view of a gyroscopic motor 800 inaccordance with an alternative preferred embodiment of the presentinvention is shown. As shown in FIG. 8, instead of using a plurality ofrotating rings, gyroscopic motor 800 employs six solid body masses,similar to a flywheel. This configuration has several advantages overthe ring design. First, it is simpler to construct, assemble andoperate. Additionally, the mass of the flywheel can be made larger andcan be more densely compacted into a smaller space, allowing for anoverall reduction in the size of gyroscopic motor 800.

At the most basic level, gyroscopic motor 800 comprises a flywheel 805inserted into a frame 810 which comprises four side plates or flanges835. Flywheel 805 will provide propulsion in much the same manner aspreviously discussed in conjunction with the rotating rings described inFIG. 6 and FIG. 7.

Flywheel 805 rotates on axle 870 and flywheel 805 is enclosed in frame810 by faceplate 865. Motor coil assemblies 845 and magnets 850 servethe same purpose as the motor coils previously discussed in conjunctionwith FIG. 3 and FIG. 4 above. Hall Effect sensors 840 are used toprovide the appropriate timing for effecting the rotation of flywheel805, which is positioned against wheel bearing 855, allowing for therotation of flywheel 805 within frame 810. C-rings 801 and spacers 860are provided to stabilize and connect the various components together.

Referring now to FIG. 9, an exploded view of a gyroscopic propulsionunit 900, assembled from six gyroscopic motors 800 of FIG. 8 isdepicted. As shown in FIG. 9, axle for each gyroscopic motor 800 isinserted into a hub 910 and hub 910 provides a fixation point andsupport for each axle.

Referring now to FIG. 10, a fully assembled gyroscopic propulsion unit900 is depicted. It should be noted that gyroscopic propulsion unit 900is connected to a computer control system (not shown this FIG.), such asthe one depicted in FIG. 11 below. This allows the rotation of eachflywheel 805 to be monitored and controlled. As previously discussed inconjunction with the rotating rings above, when the rate of rotation forthe six spinning flywheels reaches the appropriate level, the compositestructure of the six associated flywheels resists any change inorientation from any external force, including the gravitational fieldof the earth or other bodies large enough to generate a significantgravitational field.

Accordingly, as the earth spins about its axis, the gyroscopicpropulsion unit moves in the only direction possible, which is up, oraway from the center of mass for the body exerting the gravitationalforce. By adjusting the angular momentum of each of the flywheelsrelative to the other flywheels, altitudinal and directional changes ofthe gyroscopic propulsion unit can be achieved. Each of the sixgyroscopic flywheels housed within a frame may also be called a “gyroactuator.”

Referring now to FIG. 11, a block diagram of a control system 1100 for agyroscopic propulsion apparatus according to a preferred embodiment ofthe present invention is shown. The main purpose of control system 1100is to work with the drive electromagnetic drive components of thegyroscopic propulsion apparatus and thereby control a direction ofrotation and a rate of rotation for each of the masses used in thevarious preferred embodiments of the gyroscopic propulsion units of thepresent invention.

As shown in FIG. 11, control system 1100 most preferably incorporates acomputer 1105; an I/O interface 1135; an interface 1145; a bus 1195; adrive circuit 1170; a control circuit 1180; and a Hall Effect sensorcircuit 1190. As those skilled in the art will appreciate, the methodsand apparatus of the present invention apply equally to any computersystem and combination of circuit components. Specifically, it isenvisioned that a hand-held computer or palm-computing device mayperform all or substantially all of the functions described inconjunction with computer 1105.

Alternatively, control system 1100 may be implemented with a FieldProgrammable Gate Array (FPGA), digital control circuitry, or other typeof circuit mechanism. Regardless of the specific implementation, it isdesirable that there be some mechanism provided whereby the rate ofrotation and angular relationship of the three ring-like gyroscopes canbe controlled. In some applications, control system 1100 may becontained within the housing and the various control signals necessaryto control gyroscopic propulsion units 600 and 900 and may betransmitted to and from control system 1100 from an external source viawireless communication means (e.g., Wi-Fi, IR, etc.).

Computer 1105 suitably comprises at least one Central Processing Unit(CPU) or processor 1110, a main memory 1120, a memory controller 1130,and an I/O interface 1135, all of which are interconnected via a systembus 1160. Note that various modifications, additions, or deletions maybe made to control system 1100 and computer 1105 as illustrated in FIG.11 within the scope of the present invention such as the addition ofcache memory or other peripheral devices. For example, computer 1105 mayalso include a monitor or other display device (not shown) connected tothe system bus 1160. Alternatively, it is anticipated that computer 1105may be a terminal without a CPU that is connected to a network as anetwork computer (NC). In that case, the responsibilities and functionsof CPU 1110 will be assumed and performed by some other device on thenetwork. FIG. 11 is not an exhaustive illustration of any specificcontrol system, computer system or configuration, but is presented tosimply illustrate some of the salient features of one preferredembodiment for control system 1100.

Processor 1110 performs the computation and control functions ofcomputer 1105, and may comprise a single integrated circuit, such as amicroprocessor, or may comprise any suitable number of integratedcircuit devices and/or circuit boards working in cooperation toaccomplish the functions of a processor. Processor 1110 typicallyexecutes and operates under the control of an operating system 1122within main memory 1120.

I/O interface 1135 allows computer 1105 to store and retrieveinformation from drive circuit 1170, control circuit 1180, and HallEffect sensor circuit 1190 via bus 1195. It is important to note thatwhile the present invention has been (and will continue to be) toinclude a fully functional computer system, those skilled in the artwill appreciate that the various mechanisms of the present invention arecapable of being distributed as a program product in a variety of forms,and that the present invention applies equally regardless of theparticular type or location of signal to control the apparatus. I/Ointerface 1135 may be a single bus or multiple computer bus structures.Additionally, I/O interface 1135 may communicate via serial or parallelpresentation of the data using any type of communication protocol andphysical connection, including RS-232, Universal Serial Bus (USB) or anyother standard connection means known or developed by those skilled inthe art.

Interface 1145 is a connection interface for connecting keyboards,monitors, trackballs and other types of peripheral devices to computer1105. Although shown as a single interface, interface 1145 may actuallybe a combination of interface connections, each with a separateconnection to bus 1160.

Memory controller 1130, through use of a processor (not shown) separatefrom processor 1110, is responsible for moving requested informationfrom main memory 1120 and/or through I/O interface 1135 to processor1110. While memory controller 1130 is shown as a separate entity, thoseskilled in the art understand that portions of the function provided bymemory controller 1130 may actually reside in the circuitry associatedwith processor 1110, main memory 1120, and/or I/O interface 1135.

Although computer 1105 depicted in FIG. 11 contains only a single mainprocessor 1110 and a single system bus 1160, it should be understoodthat the present invention applies equally to computer systems havingmultiple processors and multiple system buses. Similarly, although thesystem bus 1160 of the preferred embodiment is a typical hardwired,multi-drop bus, any connection means that supports bi-directionalcommunication in a computer-related environment could be used, includingwireless communication means.

Main memory 1120 suitably contains an operating system 1122 and a mastercontrol program 1125. The term “memory” as used herein refers to anystorage location in the virtual memory space of computer 1105. It shouldbe understood that main memory 1120 would not necessarily contain allparts of all mechanisms shown. For example, portions of operating system1122 may be loaded into an instruction cache (not shown) for processor1110 to execute, while other related files may well be stored onmagnetic or optical disk storage devices (not shown). In addition,although shown as a single memory structure, it is to be understood thatmain memory 1120 may consist of multiple disparate memory locations.

Operating system 1122 includes the software, which is used to operateand control computer 1105. Operating system 1122 is typically executedby processor 1110. Operating system 1122 may be a single program or,alternatively, a collection of multiple programs, which act in concertto perform the functions of any typical operating system, whichfunctions are well known to those skilled in the art.

Master control program 1125 is the overall control program for controlsystem 1100. Master control program 1125 communicates with drive circuit1170, control circuit 1180 and Hall Effect sensor circuit 1190 via bus1160 and bus 1195. Master control program 1125 is capable ofinterpreting the various signals received from I/O interface 1135 andtranslating the signals in order to operate a gyroscopic propulsionapparatus. Master control program 1125 further incorporates a userinterface, which allows an operator to send instructions via bus 1195,thereby controlling the operation of a gyroscopic propulsion device. Theuser may interact with master control program 1125 by use of a videodisplay terminal and keyboard (not shown), which may be connected viainterface 1145.

Bus 1195 is any communication path or medium used to transmit signalsand provide communication between computer 1105, drive circuit 1170,control circuit 1180 and Hall Effect sensor circuit 1190. This includesstandard serial and parallel bus structures, regardless of the physicaltopology of the communication path or physical medium used. In at leastone preferred embodiment of the present invention, bus 1195 is awireless communication signal.

Drive circuit 1170 contains a power supply 1175 which may be physicallyconnected to coils 410 (in the case of gyroscopic propulsion unit 600)and motor coil assemblies 845 (in the case of gyroscopic propulsion unit900) and is used to deliver approximately 2-8 amps at 90-180 volts,thereby causing rotors 220 or flywheels 805 to rotate. Those skilled inthe art will understand that the operation of drive circuit 1170 tocontrol the rate of rotation for rotors 220 is similar to the operationof a standard brushless motor. Drive circuit 1170 delivers the preciseamount of electricity to coils 410 at precisely the right time.

Control circuit 1180 is a timing circuit that is used to calculate thespeed of rotors 220 or flywheels 805 and communicates with drive circuit1170 to control the timing for operating the gyroscopic propulsionapparatus.

Hall Effect sensor circuit 1190 relays information from Hall Effectsensors 420 or 840 and is used to monitor and locate the position ofmagnets 350 with respect to coils 410 as rotor 220 rotates. The locationof magnets 350 is sent to master control program 1125 for additionalprocessing. This allows master control program 1125 to send signals tocontrol circuit 1180 and control circuit 1180 will communicate withdrive circuit 1170 which will energize coils 410 in the appropriatesequence at the appropriate time to each drive rotor 220, therebycreating the angular momentum of superstructure 600. While the controlsare shown as separate circuits, drive circuit 1170, control circuit1180, and hall effect sensor circuit 1190 may be combined into a singlecircuit and integrated with a computer 1105 for certain applications.

Referring now to FIG. 12, a schematic diagram of a vehicle 900incorporating a gyroscopic propulsion apparatus in accordance with apreferred embodiment of the present invention is shown. Vehicle 1200 ismerely representative of any type of vehicle known to those skilled inthe art and may take the shape or form thereof. Vehicle 1200 willpreferably have one or more gyroscopic propulsion units 600. Mostpreferably, Vehicle 1200 will have at least two gyroscopic propulsionunits 910, where each gyroscopic propulsion unit 910 is configured andcontrolled as described in conjunction with FIGS. 1-8.

The presented embodiment of this device is based on six identical motorassemblies that can be placed in identical association with respect toone another forming the six faces of a cube-like device. The rotorflywheels and all other components of the resulting six motor assembliesare all identical in size, shape, and material composition. Each of thesix motors operate on a set of electrical circuits that have electricleads to the motor device from electronic motion control circuits somedistance from the motor assemblies themselves. A final master controlcircuit coordinates and operates the six individual motor controls intandem.

Each of the six motor assemblies are most preferably designed andmanufactured so that the containment, mounting, suspension, and statorcomponents have the minimal mass possible with the rotor flywheelcomponent designed and manufactured as maximally massive as possible, inrelative terms. The six assemblies in association are not mounted orotherwise restrained except to each other.

The drawings of the six motor assemblies are based on the same kind of abrushless motor design as the ring motors with analogues components sothat the same electronic circuits can drive both devices. Any brushmotor design would also work to accelerate the rotor flywheels as wellas non-electrical methods such as air or pneumatic drives. Turbinetechnologies using fuel based engine designs could also provide thedrive mechanism. Any method used to turn a wheel at high angularvelocity is acceptable so long as the collective drive, suspension, andcontainment mass is substantially less than the rotor mass.

The cube based gyroscopic propulsion unit of the present invention isable to produce additional combinations of force association that thethree ring geometry disclosed in U.S. Pat. No. 7,121,159 and U.S. Pat.No. 6,705,174 cannot. The paired or opposite rotors can spin in the samedirection or in complementary or opposite directions. They can also spinat potentially six different velocities making for a larger number ofpossible combinations of differential force association for theadditional potential of overall motion control.

While the present invention has been particularly shown and describedwith reference to preferred exemplary embodiments thereof, it will beunderstood by those skilled in the art that various changes in form anddetails may be made therein without departing from the spirit and scopeof the invention. For example, the exact number of windings used tocreate the brushless motors and the implementation of the controlcircuitry allow for many variations and equivalent embodiments withoutvarying in significance. Similarly, the size of the various gyroscopicactuators or motors is limited only by the cost and manufacturinglimitations associated with increasing the size of the gyroscopicactuators and the availability of suitable material for ensuring thatthe density of the rings creates the desired equal angular momentum foreach gyroscopic ring at any given angular velocity. Finally, it isanticipated that advances in the art of suspended rotors will eventuallyallow the creation of a propulsion system where there is no physicalcontact between the rotor and the stator element. In this case, therotor would be held in place by magnetic fields or other mechanisms.

1. An apparatus comprising: a first pair of masses configured to rotatein a first plane; a second pair of masses configured to rotate in asecond plane; a third pair of masses configured to rotate in a thirdplane; and a control program, said control program being configured tocontrol a direction of rotation and a rate of rotation for each of saidfirst pair of masses and said second pair of masses and said third pairof masses.
 2. The apparatus of claim 1 wherein said first pair of massescomprises a first pair of ring-like masses and said second pair ofmasses comprises a second pair of ring-like masses and said third pairof masses comprises a third pair of ring-like masses.
 3. The apparatusof claim 1 wherein said first pair of masses comprises a first pair offlywheels and said second pair of masses comprises a second pair offlywheels and said third pair of masses comprises a third pair offlywheels.
 4. The apparatus of claim 1 wherein: said first pair ofmasses generates a first angular momentum; said second pair of massesgenerates a second angular momentum; said third pair of masses generatesa third angular momentum; and said first, second, and third angularmomentums are equal.
 5. The apparatus of claim 1 wherein: said firstplane is substantially perpendicular to said second plane and said thirdplane; and said second plane is substantially perpendicular to saidthird plane and said first plane.
 6. The apparatus of claim 5 whereinsaid first, second, and third angular momentums are equal.
 7. Theapparatus of claim 1 further comprising a housing, said housingcontaining said apparatus.
 8. The apparatus of claim 1 furthercomprising a vehicle, said vehicle being propelled by said apparatus. 9.The apparatus of claim one further comprising a plurality of coils andmagnets, said plurality of coils and magnets being configured to rotatesaid first pair of masses and said second pair of masses and said thirdpair of masses.
 10. A method comprising the steps of: rotating a firstpair of masses in a first plane, said first pair of ring-like massgenerating a first angular momentum; rotating a second pair of masses ina second plane, said second pair of masses generating a second angularmomentum; and rotating a third pair of masses in a third plane, saidthird pair of masses generating a third angular momentum.
 11. The methodof claim 10 wherein: said first plane is substantially perpendicular tosaid second plane and said third plane; said second plane issubstantially perpendicular to said third plane; and said first, second,and third angular momentums are substantially equal.
 12. The method ofclaim 10 further comprising the step of using a control program tocontrol a rate of rotation and a direction of rotation for each of saidfirst pair of masses and said second pair of masses and said third pairof masses.
 13. The method of claim 10 further comprising the step ofvarying said first, second, and third angular momentums by activating acontrol program.
 14. The method of claim 10 wherein said steps ofrotating said first pair of masses and said second pair of masses andsaid third pair of masses comprises the steps of using a plurality ofmagnets and coils to rotate said first pair of masses and said secondpair of masses and said third pair of masses.
 15. The method of claim 10wherein said first pair of masses comprises a first pair of ring-likemasses and said second pair of masses comprises a second pair ofring-like masses and said third pair of masses comprises a third pair ofring-like masses.
 16. The method of claim 10 wherein said first pair ofmasses comprises a first pair of flywheels and said second pair ofmasses comprises a second pair of flywheels and said third pair ofmasses comprises a third pair of flywheels.
 17. The method of claim 10wherein said apparatus is contained within a housing.
 18. The method ofclaim 17 further comprising the step of controlling a vehicle attachedto said housing.